FR2524861A1 - Parachute system including vented canopy - comprising trapezoidal sections with carrying lines passing through rings through which one branch of control line also passes - Google Patents

Abstract

The parachute system includes a canopy (1) with vents (23,24). The canopy pattern is formed by two groups of trapezoidal sections (3-7) interconnected along a keel line (8). Carrying lines (12,13) are secured to the free side edges of the sections and the keel line. Two rings (16) through which the carrying lines are passed are interconnected by a member (17) connected to an extraction parachute (19). Control lines (14) include two branches at their upper end portions by which the control lines are connected to respective carrying lines in the vicinity of the rings. The branches extend in directions opposite to each other. Each control line embraces a respective ring in such a manner that it is disposed outside the ring and its lower branch is passed through the ring.

Description

PAPACHUTE SYSTEM
the present invention relates to devices for transporting loads by air, and in particular parachute systems.

The invention can be applied with maximum efficiency as a reserve parachute, usually used in conjunction with the main parachute and intended for load-bearing in the event of failure of the main paracbute. The application of the invention is particularly effective when the wind speed near the ground surface exceeds 7
Ie parachute object of the invention can also be used as a main parachute, for the delivery of a load by air to a predetermined point in space.

 We know a parachute, yes it includes a single wing. the wing development is made up of two groups of trapezoidal sections. The trapezoidal sections of each troop consist of smaller subsections, - assembled together at the lateral sides.

 The trapezoidal sections are assembled together so that the large base of each of them is adjacent to the small base of the neighboring section. Where the elements of each group are adjacent to each other, there are 9 vents.

 The sections of the two grouses are joined together along one of the lateral edges with the formation of the keel line.

 Ia wing has supporting lines intended for the fixing of the load. The upper ends of one part of the load-bearing lines are fixed to the free lateral edges of the sections1 and the upper ends of the other part of the load-bearing lines are fixed to the spine line of the figure. the trailing edges of the sections have no lines.

the lower ends of the load-bearing lines are coupled to the load (to the operator).

 the load-bearing lines have such lengths that, when the plane descends from the airfoil, they provide traction for the lateral edges and the keel line of the airfoil to give the airfoil a relatively low domed configuration.

 the wing is equipped with two control halyards.

the control halyards are intended for controlling the airfoil in the air, with a view to maneuvering the parachute and conveying the load to a predetermined point in space.

 the control halyards are fixed by their upper ends aw: load-bearing lines starting from the points of intersection of the trailing edges of the wing relative to the direction of the planed descent of the parachute, and of its lateral edges.

 Your lower ends of the control crisses remain free and the operator pulls or releases them when ordering the wing.

 Ie parachute is equipped with an extractor (extractor parachute), intended to pull the wing with the bers lines of 11 envelope and to introduce it into the air flow.

the extractor is of any known design (see, for example, U.S. Patent 3,498,565 from 1970,
Int. Cl. R64d 17/18, 17/34).

 In the known parachute, it appears to the inflation of the airfoil of great aerodynamic forces, conditioned by the configuration. Aliform to convex relatively weak. The airfoil deployed with the free being is plane, and it is the load-bearing lines attached to its lateral edges and to its keel line which give it the aliform configuration, so that at the Swelling there is a flow of channeled air coming out from under the wing. Ie ducted air flow straightens the edges of the airfoil and escapes from below the airfoil thus ensuring its gliding flight. the airfoil is then instantly inflated, which produces great aerodynamic forces, absorbed by the load as a dynamic shock.

 the objective of the invention was to create a parachute system, in which the load-bearing lines would be grouped, and the control halyards would be produced and linked to the load-bearing lines in such a way that a reduction in the dynamic loads to the inflation was obtained of the air rare airfoil, the design of the parachute remaining sufficiently single and reliable.

 the solution consists of a parachute system, comprising a canopy with vents, the development of which consists of two groups of trapezoidal sections, assembled together so as to form a keel line, load-bearing lines whose upper ends are fixed to the edges free lateral sections and to the keel line of the wing, and the lower ends are intended for coupling t 12 load, control halyards whose upper ends are fixed to the bearing supports leaving these points of intersection of the edges of flight of the airfoil, with respect to the direction that the planed descent of the parachute, and of the free lateral twists of the sections, thus or 'an extractor (parachute extractor), s-stc-me of parachute in which, according to the invention , there are provided deai rings, through each of which pass the above bearing sections of each group, these rings being connected together by a link to which the extractor parachute is linked; the upper end of each control halyard is made up of those branches with the help of which each control halyard is fixed to the corresponding supporting hanger, these branches extending in opposite directions relative to the star ; each control halyard bypasses its respective ring so that it is outside of said ring, and its lower branch passes through this ring.

 Such a group of load-bearing lines using rings, linked together by a link intended to keep these rroups at a certain distance from each other, ensures the tightening of the edges of the airfoil and the training for the air from an entry under the wing of relatively small section. This ensures a slow swelling of the airfoil and, consequently, a lowering of the aerodynamic forces on the parachute.

 Ia indicated implementation of the control halyards allows to obtain a more secure retention of the rings, in which are engaged the groups of load-bearing lines, at a certain distance from one another and at a certain distance from the wing.

 Ia determined arrangement of the rings with respect to the airfoil is ensured Thanks to the fact that, at the place where the control halyard is transferred to the corresponding bearing hanger, the control halyard bypasses its respective ring by remaining outside this ring , the lower branch of its tip compacting through this ring. Such circumvention of the control halyard, with passage of the lower branch of its end through the ring and attachment to the load-bearing hanger ensures the formation of a loop which prevents the sliding of the ring towards the baut and thus connect it to a determined position rar compared to 3a wing.

 Ia attachment of the extractor to the link denying the rings ensures the maintenance of the rings in the high position when the airfoil begins to inflate.

 It is advantageous that the sections of the two croups which are the last in the direction of the planed descent of the parachute are cut obliquely, so that their free lateral edges make a certain angle with the direction of the lateral edges of the preceding sections.

 When the supporting lines passing through the rings, and the parachute control halyards are thus produced, it is particularly advantageous that, in the two groups of wing sections, the last in the direction of the planed descent of the parachute are cut obliquely as described, because this prevents the engagement of these wing sections in the rings when the wing is deployed.

 It has been established experimentally that such a design of the parachute makes it possible to produce the much shorter carrying lines, this yes is particularly important when the parachute which is the subject of the invention is used as a reserve parachute. An emergency parachute with much shorter lines is reliable, even if the unopened main rarachute has not detached from the load.

 Otherwise, the rings can get stuck on the airfoil, which will not inflate completely, which could be the cause of a parachute failure.

 In addition, the wing sections cut obliquely ensure better channeling of the air flow at the outlet from below the wing; that is to say the formation of an air flow which does not disperse when it follows the oblique sections of the airfoil, due to the reduction in the length of the trailing edge ar by which the flow of The ducted air exits from below the airfoil. Your speed of air flow exiting from below the airfoil is increased, resulting in an increase in the overall speed of movement of the airfoil and the road stability of the airfoil. wing. specialists working in this branch of technology know that by road stability is meant the rigorously directed displacement of the airfoil.

 It is recommended that the vents are made in the last and penultimate section of the two groups, in the direction of the planed descent of the parachute, in site areas symmetrically with respect to the keel line.

 when the supporting lines passing through the rings, and the control halyards of the parachute are thus produced, it is particularly advantageous that the air vents of the airfoil are arranged as described, since, when the airfoil begins to inflate, said airfoils rings being in their high position, the main aerodynamic force resulting from the air pressure is applied to the last and the penultimate section of the two groups, in the direction of the planed descent.

 Thanks to the escape of air through said vents, when their action is carried out in conjunction with that of the rings through which the load-bearing lines pass, a notable reduction in aerodynamic force is obtained on the parachute.

 A favorable effect is obtained when the vents have the form of slits and are arranged in each group in rows, at the junction of the last section with the penultimate and the penultimate with the previous one, in the direction of the planed descent of the parachute, the ratio between the length of the row of vents at the junction of the forewarm and the previous section and the length of the row of vents at the junction between the penultimate section and the last section being between about 1.8 and about 1.2.

 If the rows of vents are produced with a length ratio greater than 1.8, the vertical descent speed of the parachute staccrolt, and if they are produced with a length ratio less than 1.2, this is the dynamic stress increasing parachute.

 Such arrangement of the vents is the most convenient for making the canopy.

 In this way, the parachute produced according to the invention undergoes aerodynamic forces which are much more reliable when the airfoil is inflated, which gives it a sufficiently high reliability in multiple reuse.

 The parachute which is the subject of the invention is of sufficiently simple and reliable design, making it possible to use it with particular effectiveness as a reserve parachute, in conjunction with a main parachute having a high aerodynamic finesse, by which is meant a high speed of horizontal movement combined with a low speed of vertical descent.

 Used as a reserve parachute, the parachute which is the subject of the invention is reliable in operation, even if the main parachute in Gefaillance has not detached from the load.

the particulars indicated and other advantages of the invention are made clearer by the description below of a concrete embodiment and by the drawings appended, in which:
FIG. 1 schematically represents an overall view of a parachute according to the invention,
FIG. 2 represents the development of the airfoil of a parachute according to the invention, the lines fixed to the line of the keel being shown by broken lines;
Figure 3 shows the detail A of Figure 1 on a larger scale.

 the parachute according to the invention has a wing 1 (Figure 1) whose development 2 (Figure 2) consists of two groups (left and right in Figure 2, no.

marked) with sections 3, .4, 5, 6, 7, of trapezoidal shape.

sections 3, 4, 5, 6, 7 have different surfaces, and they are assembled in two groups, so that section 3 of each troop with the smallest surface is the first in the Croup, in the direction the descent of the parachute.

 the trapezoidal sections 3, 4, 5, 6, 7 are assembled together so that the large bcse of each smaller surface section is joined to the small bese of a larger surface section. the common side edges of sections 3, 4, 5, 6, 7 of the two groups constitute the line 8 of the ear, and the free lateral edges of sections 3, 4, 5, 6 of the two groups lie on a straight line 9 joint, which is the lateral edge of the blade 1.

 sections 7, which are the last in the direction of the planed descent of the parachute, are cut obliquely, so that their free lateral edge 10 makes an acute angle OC, of about 450, with the direction of line 9 on which are there free side edges of sections 3, 4, 5, 6 of wing.

 The assembly of the trapezoidal sections 3, 4, 5, 6, 7 of the two groups is carried out by seams, with application of reinforcing strips (not shown).

 the free bases of the trapezoidal sections 7 constitute the edge 11 of the airfoil 1, rear in the direction of the planed descent of the parachute.

 Ie parachute also has supporting lines 12 and 13, for the suspension of the wing 1 of the load (not shown), yes, in this case, is the operator. The number of load-bearing lines 12 is chosen in accordance with.

the total area of sections 3, 4, 5, 6, 7, of the two groups and, in this case, it is equal to twelve. the upper ends of the supporting lines 12 are fixed to the free lateral edges @ of sections 7, 4, 5, 6, 7 of the two groups, at the points of intersection of the bases of sections 3, 4, 5, 6, 7 and of the straight line 9, and at the intersection points of the free lateral edges of the sections 7 and of the trailing edge 11 of the wing.

 Ie number of load-bearing lines 13 is also chosen in accordance with the total area of sections 3, 4, 5, 6, 7 of the two groups, and it is also equal to twelve. the supporting lines 13 are fixed two by two, by their upper ends, to the line keel 8, at the points or the bases these trapezoidal sections 3, 4,), 6, 7 intersect the line of eye 8.

 the supporting lines 12 and 13 are fixed to the wing 1 of the pa @ achute by sewing at the known zigzag point. the lower ends of these six load-bearing lines 12 and of the six load-bearing lines 13 of each group of sections 3, 4, 5, 6, 7 are joined in a bundle and fixed to half-loops 12a (FIG. 1), to which the belts are fixed 13a of the harness.

 Your supporting lines 12, 13 have a length such that they ensure in the air a traction of the lateral edges 9 and ae the line 8 of the ear giving the wing structure.1 a relatively low domed configuration.

 Ie parachute comprises two halyards 14 (Figure 1) control, for controlling the planed descent of the parachute. the control halyards 14 are made with a braided cord. the upper ends of the control halyards 14 are fixed by any suitable method, by means of sewing points, to the support beams 12 starting from the points of intersection of the trailing edges II with the free lateral edges 10 of sections 7.

 On the lower ends of the control halyards 14 are fixed rings 15, intended to be held by the dwarfs. due to the operator.

 Ie parachute has two rings 16 (Figures 1, 3), through which pass the supporting lines 12, 13.

These rings are made of rigid material and their surface is polished.

 In each of the rings 16 pass the supporting lines 12, 13 to one of the groups of sections 3, 4, 5, o, 7 of the airfoil 1. the rings 16 are interconnected by a link 17. The link 17 is made with a flexible material and is in the form of a textile strip. the link 17 is connected by a flexible link 18 (Figure 3) to the extractor parachute 19 (Figure 1). the flexible link 18 passes through an orifice (not shown) in the airfoil 1. The extractor parachute 19 serves to pull from its envelope (not shown) the airfoil 7 with the lines 12, 17, 14 and to introduce it into the air flow. Ie extractor chute can be of any suitable known design and have a mechanism G spring (not shown) for its introduction into the air flow.

 the upper ends of the control halyards 14 are made up of two branches: an upper branch 20 (line 3) and a lower branch 21, by means of which each control halyard 14 is fixed to the corresponding supporting hanger 12.

 the upper branch 20 and the lower branch 21 of each halyard 14 of control extend in opposite directions on the supporting hanger 12 to which they are fixed.

 Each control halyard 14 bypasses its respective ring 16 so that it is outside this ring 16, and its lower branch 21 passes through the ring 16, forming a fold of the halyard 14 relative to at its lower branch 21.

 Ies rings 16, connected by the link 17, have the function of grouping the supporting lines 12, 13 and keeping them at a determined distance from each other. Such an azure design tightens all the edges of the airfoil 1, in order to slow its swelling and, by that itself, to lower the aerodynamic forces on the psrachute.

 In such a parachute, the realization of the sections 7 of the airfoil 1 with an oblique cut eliminates the possibility of engagement of a part of the airfoil 1 in the rings 16 and gives the parachute a sufficiently high capacity for function.

 In the wing 1 of the parachute, at the junctions of sections 6 and 7 of the two groups are made vents 22 (FIG. 2), arranged symmetrically with respect to the keel line 8. In the case under consideration, the vents 22 are produced in the form of portions 23 which are not sewn and they constitute two rows 23, 24 of vents at the junctions of the sections 5, 6, 7. the vents 22, being in the form of slots, can also be produced by raking cuts in the fabric of the airfoil and by reinforcing the twists of these cuts with a strip (not shown).

 Ie ratio between the length of the row 23 of vents 22 of the airfoil I and that of the length of the row 24 of vents 22 is 1.5.

 Such an arrangement of the vents 22 ensures at the start of the inflation of the airfoil 1 the escape of the air through them, this being effected in conjunction with the action of the rings 16 through which the bearing lines 12, 13 and, pass, in this way, a reduction in the aerodynamic force is obtained on the wing 1.

 the situation of the vents 22 at the junctions of sections 5, 6, 7, that is to say of the last, the penultimate and that preceding it in the direction of the planned descent, is the most convenient for the production and the ratio of the lengths of rows 23 and 24 for this wing is 1.5.

 Ie parachute according to the invention is folded for use in an envelope (not shown), which is a parachute bag of any known design. When the envelope of the parachute is opened by hand (or automatically), the extractor 19 is ejected from the envelope by the spring mechanism and enters the air flow, where its airfoil (not seen) is deployed.

 the extractor @@ tends the link 18, which, in turn, tends the link 17 connecting the rings 16. the link 17 with the rings 16 raises the airfoil 7 located in the envelope and brings it out in the air flow, while pulling the lines 12, 13 and the halyards 14 out of the envelope.

 Under the action of the pulling force of the extractor 19, the supporting lines 12, 13 are stretched and are held together in two groups by the rings 16, at a certain distance from each other. the rings 16 abut against the fold of the control halyard 14 formed by its lower branch 21 and stop at their high position. All the edges of the airfoil 1 are then tightened and form for the air only a small entry under the airfoil 1. the air flow passing through the entry formed slowly inflates the airfoil 1. This follows the progressive straightening of the edges of the wing 1.Te straightening of the lateral edges, being on line 9, and of the trailing edges II of the wing 1 causes a slow sliding of the rings 16 along the bearing lines 12, 13, towards load.

 the extractor 19, due to its tensile force, tends to retain the rings 16 in the high position. This tensile force is due to the resistance which the air flow opposes to the inflated extractor 19 and to the mass of the load.

 the slow sliding of the rings 16 along the supporting lines 12, .13 also results from their friction on these lines 12, 13 .. During the inflation of the airfoil 1, the lines 12, 13 are gradually released from the rings 16 which bring them together , these rings 16 descending along the lines 12, 13, towards the half-loops 12a. the air intake under the wing 1 increases. the airfoil 1 gradually inflates; its lateral edges being on its lines 9 and the keel line 8 are drawn and the airfoil ultimately takes on a relatively low aliform to domed configuration.

The trailing edge 7 of the airfoil 1, not linked to the lines, channels the air flow exiting from below the airfoil 1. The air flow exits from below the airfoil 1 through the trailing edge 11 thanks to the fact that the lateral edges located on line 9 are drawn towards the load and located lower than the trailing edge 11, which is open for the exit of air. The air flow exiting under the trailing edge 11 ensures the planed descent of the parachute in the opposite direction to that in which the channeled air flow comes out from below the airfoil 1. The airfoil 1 then has a final speed of horizontal movement forward,
When the operator pulls the two control halyards 14, there is symmetrical traction of the lateral edges being on line 9, which causes a change in configuration of the wing 1. the ducted air flow leaving from below the airfoil 1 then partially disperses, because it then escapes not only from below the trailing edge 11 of the airfoil 1, but also from below its lateral edges being on the line 9. This results in a decrease in the horizontal movement speed.

 When the operator pulls the control halyard 14 on the right or on the left, there is respectively traction of the lateral edge on the right or on the left being on line 5, in FIG. 2, the airfoil I becomes asymmetrical with respect to the flow air coming out from below, this yes causes the wing 1 to turn in the corresponding direction.

 The speed of the turn of the wing 1 depends on its speed and on the value from which the control halyards 14 are drawn.

 By carrying out the maneuvers indicated with the control halyards 14, the operator maneuvers the airfoil 1 in the air, in order to convey the load to a predetermined point in space.

 For the safe landing of the load, i1 must, before landing, orient the wing 1 rigorously against the wind and thus slow its horizontal movement using the wind.

 The test model of the parachute which is the subject of the invention has undergone integral tests which have shown that it can be successfully used as a reserve parachute and will surely function in the event of failure of the main parachute, both at the maximum speed of use of the main training parachute only in the event of any delay in opening during the free fall of the parachutist. A special feature of this reserve parachute is its reliable operation if the failed main parachute has not come loose, which practically no rescue parachute of known design.

 Thanks to its happy design, the parachute's wing area requires a fabric area two times smaller than that of known rescue parachutes. Such a reserve parachute is easily placed on the parachutist, its small dimensions and its reduced weight mean that it does not interfere with the aim of the sarachutist when he operates in landing precision.

 the design of the parachute gives it an aerodynamic fineness of 1.1, a large recovery capacity and good sporting qualities. the 5ótt wing viral is obtained in 3.5 s. the vertical descent speed of up to 6.0 m / s guarantees the safe landing of the paratrooper both in calm weather and in the presence of a wind on the ground up to 10 m / s.

 The sufficiently high horizontal displacement speed of 6.5 m / s also contributes to obtaining better landing conditions than those given by known emergency parachutes, both in calm weather and in the presence of a wind on the ground.

 the high value of the horizontal component of the descent speed, the high aerodynamic finesse and the great maneuverability make it possible to ensure with the reserve parachute a good landing precision, both on an area prepared in advance. only on the area chosen visually during the descent. This can be done under various weather conditions and at different air temperatures, the landing conditions remaining gentle in the presence of a ground wind of up to 10 m / s.

 Thanks to its high technical characteristics, the parachute which is the subject of the invention can be used as an exhibition or exhibition parachute for the development of the method of activating the reserve parachute in the event of failure of the main parachute.

Claims (4)

 1. Parachute system, comprising a canopy (1) with vents (22), the development (2) of which consists of two @ @roups of trapezoidal sections (3, 4, 5, 6, 7), assembled between them so as to form a keel line (8), supporting lines (12, 13) whose upper ends are fixed to the free lateral edges of the sections (3, 4, 5, 6, 7) and to the line (8 ) of the wing of the wing (1), and the lower ends Make cestines to the coupling to the load, halyards (14) control whose upper ends have fixed to the supporting lines (12) starting from the points of intersection of trailing edges ('s1) of the airfoil, relative to the direction of the planed descent of the parachute, and these free lateral edges (10) of the sections, as well as an extractor (19) (parachute extractor), characterized in that it comprises two rings (16), through each of which pass the supporting lines (12, 13) of the sections (3, 4, 5, 6, 7) of each group, these rings (16) being r linked to each other by a link (17) to which the extractor (19) is linked, the upper end of each control halyard (14) is made up of two branches (20, 21) 11 with which each halyard (14) of control is fixed to the corresponding supporting hanger (12), these branches (20, 21) extending in opposite directions relative to each other; each halyard (14) has control bypasses its respective ring (16) so that it is outside of said ring (16), and its lower branch (21) passes through this ring (16).  2. Parachute according to claim 1, characterized in that the sections (7) of the two groups which are the last in the direction of the planed descent of the parachute are cut obliquely, so that their free lateral edges (10 ) make an angle with the direction of the side edges (5) of the previous sections.  3. Parachute according to claim 1, characterized in that the vents (22) are made in the last section (7) and in the penultimate section (6) of the two groups, in the direction of descent planed parachute, in areas located symmetrically with respect to the line (8) of the eye.  4. Parachute according to claim 3, characterized in that the vents (22) have the form of slots and are arranged in each LrouDe in rows (23, 24), at the junction of the last section (7) with the penultimate (6) and the penultimate section (6) with the previous one (5), in the direction of the planed descent of the parachute, the ratio between the length of the row (22) of vents ( 22) at the junction of the penultimate section (6) and the previous one (5) and the length of the row (24) of vents at the junction between the penultimate section (6) and the last section (7) lying between about 1.8 and about 1.2.